NACA 66(3)-418 (naca663418-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
|---|---|
|
Airfoil: NACA 66(3)-418 (naca663418-il) Reynolds number: 100,000 Max Cl/Cd: 25.12 at α=9.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-naca663418-il-100000-n5.txt Download as CSV file: xf-naca663418-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NACA 66(3)-418
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-14.000 -0.3652 0.10063 0.09507 -0.1067 0.9555 0.0400
-13.750 -0.3963 0.08789 0.08223 -0.1155 0.9516 0.0394
-13.500 -0.4305 0.07757 0.07170 -0.1233 0.9477 0.0388
-13.250 -0.4602 0.07069 0.06459 -0.1272 0.9414 0.0384
-13.000 -0.4842 0.06529 0.05893 -0.1294 0.9356 0.0383
-12.750 -0.5030 0.06081 0.05416 -0.1305 0.9305 0.0383
-12.500 -0.5208 0.05753 0.05063 -0.1294 0.9230 0.0383
-12.250 -0.5328 0.05437 0.04719 -0.1285 0.9176 0.0383
-12.000 -0.5441 0.05182 0.04436 -0.1265 0.9113 0.0383
-11.750 -0.5532 0.04958 0.04184 -0.1240 0.9047 0.0384
-11.500 -0.5561 0.04724 0.03918 -0.1221 0.9000 0.0386
-11.250 -0.5600 0.04542 0.03710 -0.1192 0.8941 0.0389
-11.000 -0.5598 0.04374 0.03514 -0.1165 0.8888 0.0391
-10.750 -0.5549 0.04196 0.03305 -0.1144 0.8848 0.0395
-10.500 -0.5454 0.04028 0.03102 -0.1127 0.8819 0.0402
-10.250 -0.5435 0.03930 0.02975 -0.1093 0.8769 0.0408
-10.000 -0.5233 0.03794 0.02834 -0.1090 0.8738 0.0417
-9.750 -0.5029 0.03680 0.02712 -0.1087 0.8709 0.0427
-9.500 -0.4779 0.03558 0.02575 -0.1089 0.8688 0.0438
-9.250 -0.4468 0.03425 0.02427 -0.1099 0.8672 0.0449
-9.000 -0.4137 0.03306 0.02290 -0.1110 0.8659 0.0461
-8.750 -0.3828 0.03210 0.02175 -0.1118 0.8645 0.0477
-8.500 -0.3610 0.03142 0.02114 -0.1112 0.8615 0.0493
-8.250 -0.3447 0.03096 0.02070 -0.1098 0.8578 0.0510
-8.000 -0.3259 0.03046 0.02016 -0.1087 0.8549 0.0531
-7.750 -0.3064 0.02993 0.01956 -0.1077 0.8525 0.0551
-7.500 -0.2893 0.02933 0.01894 -0.1064 0.8503 0.0569
-7.250 -0.2735 0.02878 0.01840 -0.1051 0.8483 0.0595
-7.000 -0.2566 0.02828 0.01783 -0.1039 0.8466 0.0634
-6.750 -0.2617 0.02850 0.01804 -0.0988 0.8416 0.0653
-6.500 -0.2628 0.02841 0.01797 -0.0946 0.8375 0.0683
-6.250 -0.2560 0.02817 0.01769 -0.0914 0.8344 0.0724
-6.000 -0.2461 0.02778 0.01730 -0.0888 0.8319 0.0789
-5.750 -0.2343 0.02736 0.01692 -0.0865 0.8300 0.0906
-5.500 -0.2583 0.02801 0.01760 -0.0779 0.8244 0.0933
-5.250 -0.2720 0.02833 0.01795 -0.0712 0.8197 0.1019
-5.000 -0.2722 0.02801 0.01787 -0.0668 0.8168 0.1355
-4.750 -0.2729 0.02712 0.01756 -0.0626 0.8143 0.2349
-4.500 -0.2799 0.02593 0.01707 -0.0574 0.8121 0.3685
-4.250 -0.3177 0.02713 0.01812 -0.0464 0.8050 0.3423
-4.000 -0.3301 0.02643 0.01820 -0.0399 0.8012 0.4782
-3.750 -0.3074 0.02806 0.02060 -0.0357 0.7995 0.6476
-3.500 -0.2964 0.02822 0.02060 -0.0331 0.7975 0.6856
-3.250 -0.2784 0.02928 0.02160 -0.0302 0.7961 0.7211
-3.000 -0.2495 0.03172 0.02405 -0.0266 0.7951 0.7559
-2.750 -0.2488 0.03337 0.02570 -0.0203 0.7907 0.7710
-2.500 -0.2409 0.03425 0.02653 -0.0162 0.7871 0.7817
-2.250 -0.2290 0.03441 0.02659 -0.0137 0.7841 0.7904
-2.000 -0.2108 0.03443 0.02649 -0.0124 0.7820 0.7960
-1.750 -0.1839 0.03460 0.02655 -0.0123 0.7804 0.7994
-1.500 -0.1576 0.03461 0.02645 -0.0123 0.7789 0.8035
-1.250 -0.1621 0.03446 0.02623 -0.0080 0.7747 0.8114
-1.000 -0.1558 0.03477 0.02651 -0.0047 0.7699 0.8144
-0.750 -0.1360 0.03486 0.02652 -0.0038 0.7670 0.8172
-0.500 -0.1130 0.03484 0.02643 -0.0035 0.7647 0.8201
-0.250 -0.0872 0.03474 0.02624 -0.0038 0.7629 0.8232
0.000 -0.0598 0.03457 0.02598 -0.0044 0.7613 0.8264
0.250 -0.0657 0.03485 0.02624 0.0000 0.7542 0.8302
0.500 -0.0458 0.03493 0.02629 0.0008 0.7506 0.8322
0.750 -0.0202 0.03494 0.02625 0.0007 0.7480 0.8341
1.000 0.0092 0.03489 0.02615 -0.0001 0.7461 0.8356
1.250 0.0406 0.03481 0.02602 -0.0012 0.7445 0.8370
1.500 0.0371 0.03523 0.02645 0.0026 0.7359 0.8408
1.750 0.0628 0.03522 0.02641 0.0022 0.7325 0.8428
2.000 0.0934 0.03516 0.02632 0.0010 0.7302 0.8444
2.250 0.1261 0.03508 0.02622 -0.0004 0.7284 0.8459
2.500 0.1274 0.03559 0.02676 0.0028 0.7196 0.8479
2.750 0.1533 0.03564 0.02682 0.0026 0.7160 0.8494
3.000 0.1839 0.03559 0.02678 0.0019 0.7136 0.8511
3.250 0.2168 0.03551 0.02672 0.0007 0.7118 0.8527
3.500 0.2185 0.03610 0.02734 0.0036 0.7016 0.8556
3.750 0.2485 0.03605 0.02733 0.0027 0.6984 0.8573
4.000 0.2823 0.03591 0.02722 0.0014 0.6962 0.8589
4.500 0.3196 0.03638 0.02778 0.0025 0.6826 0.8632
4.750 0.3532 0.03614 0.02760 0.0015 0.6802 0.8646
5.000 0.3592 0.03670 0.02823 0.0039 0.6694 0.8670
5.250 0.3902 0.03649 0.02810 0.0032 0.6659 0.8690
5.500 0.4246 0.03613 0.02782 0.0022 0.6634 0.8712
5.750 0.4309 0.03673 0.02850 0.0043 0.6515 0.8747
6.000 0.4657 0.03632 0.02818 0.0032 0.6484 0.8769
6.250 0.4762 0.03682 0.02877 0.0047 0.6366 0.8799
6.500 0.5097 0.03627 0.02833 0.0041 0.6330 0.8817
6.750 0.5205 0.03666 0.02883 0.0059 0.6209 0.8847
7.000 0.5558 0.03591 0.02821 0.0051 0.6171 0.8870
7.250 0.5684 0.03629 0.02870 0.0065 0.6045 0.8905
8.250 0.6563 0.03537 0.02832 0.0093 0.5612 0.9042
8.500 0.6860 0.03391 0.02690 0.0103 0.5355 0.9084
8.750 0.7242 0.03179 0.02463 0.0108 0.4842 0.9121
9.000 0.7581 0.03050 0.02304 0.0114 0.4245 0.9157
9.250 0.7733 0.03079 0.02300 0.0131 0.3628 0.9206
9.500 0.7791 0.03188 0.02372 0.0153 0.3014 0.9261
9.750 0.7819 0.03325 0.02475 0.0174 0.2413 0.9318
10.000 0.7840 0.03489 0.02601 0.0193 0.1783 0.9383
10.250 0.7874 0.03662 0.02733 0.0208 0.1194 0.9447
10.500 0.7949 0.03824 0.02871 0.0218 0.0870 0.9520
10.750 0.8066 0.03976 0.03016 0.0221 0.0710 0.9597
11.000 0.8199 0.04124 0.03166 0.0220 0.0621 0.9693
11.250 0.8298 0.04259 0.03302 0.0222 0.0563 1.0000
11.500 0.8414 0.04412 0.03461 0.0225 0.0520 1.0000
11.750 0.8517 0.04580 0.03632 0.0227 0.0485 1.0000
12.000 0.8635 0.04739 0.03798 0.0229 0.0454 1.0000
12.250 0.8742 0.04907 0.03968 0.0230 0.0433 1.0000
12.500 0.8860 0.05070 0.04137 0.0232 0.0412 1.0000
12.750 0.8995 0.05224 0.04300 0.0234 0.0394 1.0000
13.000 0.9125 0.05382 0.04461 0.0234 0.0376 1.0000
13.250 0.9260 0.05540 0.04612 0.0235 0.0363 1.0000
13.500 0.9424 0.05682 0.04769 0.0235 0.0349 1.0000
13.750 0.9584 0.05832 0.04932 0.0235 0.0335 1.0000
14.000 0.9744 0.05986 0.05093 0.0235 0.0325 1.0000
14.250 0.9910 0.06141 0.05253 0.0235 0.0317 1.0000
14.500 1.0093 0.06295 0.05408 0.0234 0.0310 1.0000
14.750 1.0255 0.06483 0.05613 0.0234 0.0304 1.0000
15.000 1.0376 0.06707 0.05860 0.0234 0.0299 1.0000
15.250 1.0464 0.06964 0.06141 0.0235 0.0295 1.0000
15.500 1.0512 0.07254 0.06457 0.0236 0.0290 1.0000
15.750 1.0525 0.07571 0.06797 0.0236 0.0286 1.0000
16.000 1.0510 0.07914 0.07163 0.0234 0.0282 1.0000
16.250 1.0472 0.08279 0.07550 0.0230 0.0278 1.0000
16.500 1.0415 0.08676 0.07970 0.0223 0.0276 1.0000
16.750 1.0339 0.09101 0.08417 0.0214 0.0273 1.0000
17.000 1.0269 0.09525 0.08857 0.0202 0.0270 1.0000
17.250 1.0155 0.10028 0.09381 0.0185 0.0268 1.0000
17.500 1.0005 0.10606 0.09983 0.0162 0.0267 1.0000
17.750 0.9837 0.11240 0.10639 0.0132 0.0266 1.0000
18.000 0.9599 0.12041 0.11466 0.0090 0.0267 1.0000
18.250 0.8892 0.13956 0.13432 -0.0026 0.0276 1.0000
|
Polar data table (+)
Polar graphs
<< Back to NACA 66(3)-418 (naca663418-il)